Arrangement for mounting radiators in aeroplane wings



Oct. 8, 1929. LEPERE 1,730,978

ARRANGEMENT FOR MOUNTING RADIATORS IN AEROPLANE WINGS Filed April 10,1929 i i r i l //V V15 N 70%? [agne fiarie o/yes Lqoere Patented Oct. 8,1929 EUGEN E GEORGES LEPERE, OF PARIS, FRANCE ARRANGEMENT FOR MOUNTINGBADIATOBS IN .AEBOPLANE WINGS Application filed April 10, I829,

The invention relates to an improved arrangement of the radiator ofwater-cooled engines for aeroplanes in the aeroplane wings.

It hasalready been proposed to mount radiators of aeroplane engines inapertures of aeroplane wings, for the double purpose of improving theaerodynamic qualities of the aeroplane, due to the fact that theradiatoris concealed, and of automatically regulating the temperature of coolinwater, inasmuch as the maximum power 0 sponds to a flight with thesteepest angle of attack, that is, to the most intense circulation ofair through the radiator, While the minimum power corresponds very smallangle of attack, in which the flow of air through the aperture is muchreduced.

Although this arrangement afforded a certain degree of self-regulationof the temperature, it has been found, however, that the aperturecontaining the radiator was a source of much disturbances in theperformance of the wings, that the maximum altitude of flight as well asthe maximum speed were greatly reduced, so that the mounting of theradiator in the wings was finally abandoned.

On the other hand, it has been found in the recent period that certainapertured wings are,

equally as efficient as plain wings, and even superior. I

The present lnvention relates to a wing for aeroplanes or the like whichcomprises one or more apertures, and it is chiefly characterlzed by thefact that in the saidaperture or apertures, whose outline is such as topreserve the proper aerodynamic features of the wing, are mounted one ormore radiators having parallel tubes or plates and so disposed thatthere will be no change in the direction of the air streams traversinthe aperture.

In the appended rawing, which is'given solely by way of example:

Fig. 1 is a diagrammatic cross section of a wing radiator arrangement ofthe known type. r

Fig. 2 is a like section of a wing having an aperture whose outline isso designed as to preserve or improve the aerodynamic qualities of thewing.

Fig. 3 is a sectional View similar to Figure a the discharge the enginecorreto a flight with a] Serial No. 354,185, and in France June 9, 1928.

2, in which a radiator ture, according to the invention.

Fig. 4 is an inverted plan view of Figure 3.

In the diagrammatic sectional view of the known arrangement, shown inFig. 1, 1 denotesthe set of radiator tubes; 2 and 3 are the collectorsfor the supply of hot water and of cooled water, res ctively. The arrowsshow the direction'o the air streams. It is readily observed that eddiesare produced in the region a b 0, while streams of air impinge againstthe rear vertical surface (1 e. For these difl'erent reasons thequalities of the wing are greatly impaired, and the above arrangementhasbeen set aside in practice.

Fig. 2 is a diagrammatic sectional view of a wing provided with an airchannel 4, of a current type. The wing is thus divided into a front part5 and a'rear part 6 whose respective rear and front outlines are suchthat the air streams are practically not deflected, as shown by thearrow.

Figs. 3 and 4 show an arrangement according to the invention, whereinthe radiator, consisting of a set of cooling members 7, is disposed inan aperture 4 of a wing quite similar to that shown in Figure 2; 8 isthe Water supply collector and 9 the collector for the discharge ofcooled water; the relative disposition of the collectors may also bereversed.

The dotted line 10 denotes an adjustable shutter, which may be providedabove the air channel and consists for example of a Persian blindarrangement or a plate which is slidable from front to rear, whereby theaperture of the wing may be wholly or'partially obturated. V The saidshutter is required only for certain classes of aeroplanes, which areadapted to travel in regions where the temperature is considerablyvariable.

The operation of the device is as follows. The air flowing-through theair channel will pass along the flat tubes of the radiator,

which are thus efficiently cooled, The air is mounted in said aperor inrising flight.

' the form ofconstruction face-by a curved surface,

, wherein said radiator tack. This self-regulation is due to the factthat the maximum power required from the engine corresponds to flight atsteep angles, that is, to the most intense circulation of air throughthe radiator, whilst the minimum power corresponds to flight at smallangles, that is, to a reduced circulation of air through the airchannel. I

'Another advantage of this arrangement resides in that the maximumaltitude and speed are little affected by the provision of the airchannel, since the radiator, which is situated in the said channel, willoccasion a loss of pressure which is favourable to the improvement ofthe qualities of the wing at the angles of attack normally employed inhorizontal Obviously, the invention is not limited to herein describedand represented, which is given solely by way of example; For instance,a wing has been represented which has but a single air channel or slot,but wings having several slots also fall within the scope of theinvention. The wing may further comprise several distinct radiators,mounted in each channel.

Having now'describedmy invention what I claim as new and desire tosecure by Letters Patent is:

1'. An arrangement for mounting the radiator of a water-cooled aeroplaneengine in the aeroplane wing, comprising a thick wing 6. An arrangementas claimed in claim 1, which further comprises an adjustable obturatingmember consisting of a series of pivoted blades at the upper part ofsaid air channel.

In testimony whereof I have signed my name to this specification.

. resins MARIE GEORGES tartan having an air channel whose outline is sodetermined as not to impair the aerodynamic qualities of the wing, and aradiator mounted within said channel and comprising radiating elementsparallel with the aeroplane axis.

2. An arrangement for mounting the radiator of a water-cooled aeroplaneengine in the aeroplane wing, comprising a thick wing having an airchannel upwardly inclined from the front to the rear, and a radiatormounted within said channel and comprising radiating elements parallelwith the aeroplane axis.

3. An arrangement for mounting the radiaftor ofa water-cooled aeroplaneengine in the aeroplane wing, comprising a thick wing having an airchannel upwardly inclined from the front to the rear and whose frontwall is connected with the wing 'underiace by a curved surface of smallcurvature, the rear wall being connected with the wing upper and aradiator mounted within said channel and comprising radiating elementsparallel with the aeroplane axis.

4:. An arrangement as claimed in claim 1,

comprises a set of parallel fiat channels of small thickness andcomparatively large width.

5. An arrangement as claimed in claim 1, which further comprises anadjustable obturating member associated with said air channel.

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